A Multi-Disciplinary Approach to Design Long Range Guided Projectiles

Vasile, Joseph D.; Bryson, Joshua T.; Gruenwald, Benjamin C.; Fairfax, Luisa D.; Strohm, Luke S; Fresconi, Frank

doi:10.2514/6.2020-1993

Cited by 6 publications

(3 citation statements)

References 8 publications

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“…Subsequent efforts have also aimed at stretching the sphere of action of land-and surface-based systems by extending the range of guided ammunition [2]. Innovative projectile designs [3] [4] have been developed in order to achieve increased range through a glide phase performed at a shallow flight path angle.…”

Section: Nomenclaturementioning

confidence: 99%

Concurrent Airframe-Controller Optimization of a Guided Projectile Fitted with Lifting Surfaces

Riss

Roussel

Laroche

2022

AIAA SCITECH 2022 Forum

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Innovative long-range guided projectiles concepts require precise flight path tracking in order to achieve maximum range and terminal accuracy. For such airframes featuring large lifting surfaces, vertical maneuvering performance relies on pitch attitude control.Thus, a challenging problem arises from the conflict between performance requirements and actuator limitations. The projectile static stability should be tailored to limit controls deflections and actuator bandwidth. This work proposes a plant-controller optimization (PCO) procedure to tune the projectile static stability and the controller gains in a single step. This methodology is applied to actuator usage minimization under control performance constraint. The optimal airframe-controller design shows superior actuator roll-off characteristics compared to the outcome of the traditional "design then control" methodology. The codesign also proves to be much less computationally intensive, which confirms the relevance of the approach.

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Section: Nomenclaturementioning

confidence: 99%

Concurrent Airframe-Controller Optimization of a Guided Projectile Fitted with Lifting Surfaces

Riss

Roussel

Laroche

2022

AIAA SCITECH 2022 Forum

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“…The supporting technology for achieving the integration of these control analyses to main-body design is the multidisciplinary design optimization (MDO) [20], which has been well suited to deal with complex interactions in various aerospace engineering systems [21−23]. However, due to guidance being paramount for missile design [24,25], these methods without guidance precision analysis [26−28] are still not sufficient for solving MM-design challenges.…”

Section: Introductionmentioning

confidence: 99%

Design Methodology of a Mini-Missile Considering Flight Performance and Guidance Precision

Zhang,

Gong,

et al. 2024

J. of Syst. Eng. Electron.

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The design of mini-missiles (MMs) presents several novel challenges. The stringent mission requirement to reach a target with a certain precision imposes a high guidance precision. The miniaturization of the size of MMs makes the design of the guidance, navigation, and control (GNC) have a larger-thanbefore impact on the main-body design (shape, motor, and layout design) and its design objective, i.e., flight performance. Pursuing a trade-off between flight performance and guidance precision, all the relevant interactions have to be accounted for in the design of the main body and the GNC system. Herein, a multi-objective and multidisciplinary design optimization (MDO) is proposed. Disciplines pertinent to motor, aerodynamics, layout, trajectory, flight dynamics, control, and guidance are included in the proposed MDO framework. The optimization problem seeks to maximize the range and minimize the guidance error. The problem is solved by using the nondominated sorting genetic algorithm II. An optimum design that balances a longer range with a smaller guidance error is obtained. Finally, lessons learned about the design of the MM and insights into the trade-off between flight performance and guidance precision are given by comparing the optimum design to a design provided by the traditional approach.

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“…Interesting properties of the analyzed concept derive from the selection of a reduced set of control actuators, leading to an asymmetric canards/fins configuration [24,25], and a predominant statically unstable behavior. Recent research on long-range guided projectiles [26] underlined the impact of the canards/fins configuration, aerodynamics modeling, and guidance development on the overall range capability. In a previous study, the full nonlinear dynamics of the projectile have been derived [27], and converted into a corresponding quasi-LPV model through the State Transformation technique [28], trying to minimize the need for model approximations.…”

Section: Introductionmentioning

confidence: 99%

Linear Parameter Varying Pitch Autopilot Design for a Class of Long Range Guided Projectiles

Vinco

Theodoulis

Sename

et al. 2023

AIAA SCITECH 2023 Forum

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Promising results on LPV design have been recently proposed, concerning the modeling and control of missiles, rockets, and aircraft. However, very few investigations have been focused on the development of guided projectile applications. This paper presents a pure linear parameter varying (LPV) modeling and control design approach intended to improve the range capability of a new class of Long Range Guided Projectiles (LRGP). The investigated concept consists of an asymmetric 155 mm fin-stabilized projectile equipped with a reduced amount of control actuators and characterized by a predominant unstable behavior across the analyzed flight envelope. The main advantages of the LPV design in terms of guaranteed robustness and stability are compared to standard gain-scheduling-based linear time-invariant (LTI) control strategies. A nonlinear simulation scenario is performed in order to assess the reliability of a pure LPV autopilot design, based on the polytopic formulation, across the entire flight envelope, over a local modal control design related to a specific set of flight conditions.

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A Multi-Disciplinary Approach to Design Long Range Guided Projectiles

Cited by 6 publications

References 8 publications

Concurrent Airframe-Controller Optimization of a Guided Projectile Fitted with Lifting Surfaces

Concurrent Airframe-Controller Optimization of a Guided Projectile Fitted with Lifting Surfaces

Design Methodology of a Mini-Missile Considering Flight Performance and Guidance Precision

Linear Parameter Varying Pitch Autopilot Design for a Class of Long Range Guided Projectiles

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